CN101063412A - Nested turbine bucket closure group - Google Patents
Nested turbine bucket closure group Download PDFInfo
- Publication number
- CN101063412A CN101063412A CNA2007101019043A CN200710101904A CN101063412A CN 101063412 A CN101063412 A CN 101063412A CN A2007101019043 A CNA2007101019043 A CN A2007101019043A CN 200710101904 A CN200710101904 A CN 200710101904A CN 101063412 A CN101063412 A CN 101063412A
- Authority
- CN
- China
- Prior art keywords
- blade
- closed
- vane
- keyway
- front side
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/31—Application in turbines in steam turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
Abstract
A closure bucket group (100) for mounting on a dovetail (140) of a turbine wheel (150). The closure bucket group (100) may include a leading bucket (110) with a leading bucket rear side (170), a closure bucket (120) with a closure bucket front side (230) and a closure bucket rear side (240), and a trailing bucket (130) with a trailing bucket front side (320). The leading bucket rear side (170) and the closure bucket front side (230) define a pair of first enclosed keyways (390) and the closure bucket rear side (240) and the trailing bucket front side (320) define a pair of second enclosed keyways (400). A number of keys (410, 420, 430, 440) may be positioned within the first enclosed keyways (390) and the second enclosed keyways (400).
Description
Technical field
The application relates generally to turbo machine and more specifically relates to the turbine bucket closure group.
Background technique
Steam turbine fin or blade shroud are provided with at regular intervals around turbine wheel.In the opening on the impeller surface of axial-entry blade one at a time, around impeller blade is circumferentially slided then blade is assembled.Blade pass is crossed the convex of cooperation and the dovetail of spill is fixed.Yet in order to seal this assembly, last blade must limit by the device except dovetail.The blade that this is last, promptly closed blade usually adopts pin to be fixed on the impeller, perhaps is fixed on its blade of vicinity by key.
Yet the flexural property of circular skirt section blade can not help them to utilize key in the solid section (dovetail just) in skirt section, is subjected to centrifugal force so that retrain closed blade.Axially the key that is provided with is also undesirable, because very little with engaging of the blade that is close to, thus the restriction shearing strength.And relatively the key of the angled setting of axis of machine may be undesirable, because the flexural property in circular skirt section produces irregular shear plane, this shear plane can be not crossing with the center of key at the thickest part place of key.This can force the use of closure blocks, and this closure blocks utilization pin is fixed on the impeller.Closure blocks does not normally have the blade of fin.By removing fin, quality and centrifugal load reduce, thereby reduce impeller pin upper stress to acceptable level.Yet, because closure blocks does not have fin, in steam passage, have opening, can produce adverse influence to performance.
Therefore need a kind of do not have under the overstress situation can support flap improved closed blade.This blade should increase overall system performance.
Summary of the invention
Therefore, the application describes the closed vane group on the dovetail be used to be installed in turbine wheel.This closure vane group can comprise the start vane with start vane rear side, has the closed blade of closed blade front side and closed blade rear side and has the afterbody blade of afterbody blade front side.Start vane rear side and closed blade front side limit the first sealing keyway, and closed blade rear side and afterbody blade front side limit the second sealing keyway.A plurality of keys can be arranged within the first sealing keyway and the second sealing keyway, so that support closed blade.
Start vane and afterbody blade can comprise a pair of hook spare that is used for the dovetail coupling.The rear side of start vane can comprise smooth axial component of start vane and a pair of start vane keyway, and these keyways are provided with respect to the impeller axis at a certain angle along the flat of pair of outer.The front side of closed blade can comprise the axial component and the anterior keyway of a pair of closed blade of the preceding portion flattening of closed blade, and these keyways are provided with respect to the impeller axis at a certain angle along the flat of pair of outer.The rear side of closed blade can comprise the axial component and a pair of closed blade rear portion keyway of portion flattening behind the closed blade, and these keyways are provided with respect to the impeller axis at a certain angle along the flat of pair of outer.Closed blade can comprise fin.The front side of afterbody blade can comprise smooth axial component of afterbody blade and a pair of afterbody blade keyway, and these keyways are provided with respect to the impeller axis at a certain angle along the flat of pair of outer.The first sealing keyway can comprise a pair of first sealing keyway, and the second sealing keyway can comprise a pair of second sealing keyway.
The application has also described the closed vane group on the dovetail that is used to be installed in turbine wheel.This closure vane group can comprise having a pair of initial hook spare so that the start vane that cooperates with dovetail, closed blade and have a pair of afterbody hook spare so that the afterbody blade that cooperates with dovetail.Start vane and closed blade can limit a pair of first sealing keyway, and closed blade and afterbody blade can limit a pair of second sealing keyway.A plurality of keys can be arranged within the first sealing keyway and the second sealing keyway, so that support closed blade.
Closed blade can comprise fin.Start vane is nested with closed blade, and the afterbody blade is nested with closed blade.
These of the application and other feature become obvious after those skilled in the art understand embodiment's following detailed description with appended claim in conjunction with the accompanying drawings.
Description of drawings
Fig. 1 is the perspective view of closed vane group described here.
Fig. 2 is the top plan view of the closed blade of Fig. 1.
Fig. 3 is the sectional view of the closed vane group of Fig. 1.
Fig. 4 is the front perspective view of start vane of the closed group of Fig. 1.
Fig. 5 is the back perspective view of start vane of the closed group of Fig. 1.
Fig. 6 is the front perspective view of closed blade of the closed group of Fig. 1.
Fig. 7 is the back perspective view of closed blade of the closed group of Fig. 1.
Fig. 8 is the front perspective view of afterbody blade of the closed group of Fig. 1.
Fig. 9 is the back perspective view of afterbody blade of the closed group of Fig. 1.
Embodiment
Referring now to accompanying drawing,, wherein identical reference character is represented identical parts in a plurality of accompanying drawings, and Fig. 1-3 shows closed vane group 100 described here.As shown in the figure, closed vane group 100 comprises start vane 110, closed blade 120 and afterbody blade 130.The blade 110,120,130 of closed vane group 100 is arranged on the dovetail 140 of turbine wheel 150.
Figure 4 and 5 show the start vane 110 of closed vane group 100.As shown in the figure, start vane 110 has front side 160 and rear side 170.Start vane comprises from platform 190 extended fins 180.Platform extends in a pair of hook spare 200.The dovetail 140 of hook spare 200 design sizes to hold turbine wheel 150.Platform 190 on the front side 160 of start vane 110 has conventional circular skirt section shape.Rear side 170 has the smooth axial component 210 that is formed on platform 190 central authorities, and wherein two keyways 220 extend on the edge of rear side 170 from smooth axial component 210.Two keyways 220 along the flat 225 of outside with respect to the angled setting of impeller axis.
Fig. 6 and 7 shows the closed blade 120 of closed vane group 100.As start vane 110, closed blade 120 comprises front side 230 and rear side 240.Closed blade 120 also comprises fin 250 and platform 260.Different with start vane 110, closed blade 120 has the relative leg 270 of a pair of and hook spare 200.Leg 270 leans on along the dovetail 140 of turbine wheel.Substitute the circular skirt section form of the platform of describing in start vane 110 190, the front side 230 of closed blade 120 comprises smooth axial component 280, and wherein a pair of keyway 290 extends on the edge of front side 230 from smooth axial component 280.Two keyways 290 along the flat 295 of outside with respect to the angled setting of impeller axis.The flat 280,295 of the front side 230 of closed blade 120 and keyway 290 can be nested with the flat portions 210,225 and the keyway 220 of the rear side 170 of start vane 110.Closed blade 120 rear sides 240 are similar to the rear side 170 of start vane 110, because it comprises smooth axial component 300 and extends to a pair of keyway 310 on the edge of rear side 240 from smooth axial component 300.Two keyways 310 along the flat 315 of outside with respect to the angled setting of impeller axis.
Fig. 8 and 9 shows the afterbody blade 130 of closed vane group 100.Afterbody blade 130 comprises front side 320 and rear side 330.Afterbody blade 130 also comprises fin 340, platform 350 and a pair of hook spare 360.The front side 320 of afterbody blade 130 is included in the smooth axial component 370 in the middle of the platform 350, and wherein a pair of keyway 380 extends on the edge of front side 320 from smooth axial component 370.Two keyways 380 along the flat 385 of outside with respect to the angled setting of impeller axis.The flat 370,385 of the front side 320 of afterbody blade 130 and keyway 380 can be nested with the flat 300,315 and the keyway 310 of the rear side 240 of closed blade 120.The rear side 330 of afterbody blade 130 comprises the platform 350 of the circular skirt section shape with common blade.
Refer again to Fig. 1-3, when being arranged on the dovetail 140 of turbine wheel 150 when the blade 110,120,130 of closed vane group 100, the rear side 170 of start vane 110 is nested with the front side 230 of closed blade 120.Similarly, the keyway 290 of the keyway 220 of start vane 110 and closed blade 120 forms the first sealing keyway 390.Similarly, the front side 320 of afterbody blade 130 is nested with the rear side 240 of closed blade 120.Similarly, the keyway 380 of afterbody blade 130 aligns with the keyway 310 of closed blade 120, so that form the second sealing keyway 400.Keyway 390,400 extends on the both sides of closed vane group 100.First key 410 can be arranged within the first sealing keyway 190, and second key 420 can be arranged within the second sealing keyway 400.Interchangeable key group, i.e. triple bond 430 and quadruple linkage 440 are arranged on the opposite side of closed vane group 100.
Sealing keyway 390,400 provides along key 410,420 the straight shear plane of 430,440 whole length.Therefore closed blade 120 is by means of key 410,420, and 430,440 fix and support.Therefore the centrifugal load of closed blade 120 is sent on guiding and the afterbody blade 110,130 in large quantities by means of hook spare 200,360.
Foregoing only relates to the application's preferred embodiment clearly, many change and be modified in this and can be obtained by those of ordinary skills under the situation that does not break away from total spirit and scope of the present invention, the total spirit and scope of the present invention are as defined in claim and its equivalent below.
100 closed vane group
110 start vane
120 closed blades
130 afterbody blades
140 dovetails
150 turbine wheels
160 front sides
170 rear sides
180 fins
190 platforms
200 hook spares
210 flats
220 keyways
The flat of 225 outsides
230 front sides
240 rear sides
250 fins
260 platforms
270 legs
280 flats
290 keyways
The flat of 295 outsides
300 flats
310 keyways
The flat of 315 outsides
320 front sides
330 rear sides
340 fins
350 platforms
360 hook spares
370 flats
380 keyways
The flat of 385 outsides
390 first sealing keyways
400 second sealing keyways
410 first keys
420 second keys
430 triple bonds
440 quadruple linkages
Claims (9)
1. the closed vane group (100) on the dovetail (140) that is used to be installed in turbine wheel (150) comprising:
Start vane (110) with start vane rear side (170);
Closed blade (120) with closed blade front side (230) and closed blade rear side (240);
Afterbody blade (13) with afterbody blade front side (320);
Wherein start vane rear side (170) and closed blade front side (230) limit the first sealing keyway (390), and wherein closed blade rear side (240) and afterbody blade front side (320) limit second and seal keyway (400); With
Be arranged on a plurality of keys (410,420,430,440) within the first sealing keyway (390) and the second sealing keyway (400).
2. closed vane group as claimed in claim 1 (100), wherein the rear side (170) of start vane (110) comprises the smooth axial component of start vane (210).
3. closed vane group as claimed in claim 1 (100), wherein the rear side (170) of start vane (110) comprises a pair of start vane keyway (220).
4. closed vane group as claimed in claim 1 (100), the front side (230) of wherein closed blade (120) comprise the axial component (280) of the preceding portion flattening of closed blade.
5. closed vane group as claimed in claim 1 (100), the front side (230) of wherein closed blade (120) comprise the anterior keyway (290) of a pair of closed blade.
6. closed vane group as claimed in claim 1 (100), the rear side (240) of wherein closed blade (120) comprise the axial component (300) of portion flattening behind the closed blade.
7. closed vane group as claimed in claim 1 (100), the rear side (240) of wherein closed blade (120) comprises a pair of closed blade rear portion keyway (310).
8. closed vane group as claimed in claim 1 (100), wherein the front side (320) of afterbody blade (130) comprises the smooth axial component of afterbody blade (370).
9. closed vane group as claimed in claim 1 (100), wherein the front side (320) of afterbody blade (130) comprises a pair of afterbody blade keyway (380).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/380049 | 2006-04-25 | ||
| US11/380,049 US7517195B2 (en) | 2006-04-25 | 2006-04-25 | Nested turbine bucket closure group |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101063412A true CN101063412A (en) | 2007-10-31 |
| CN101063412B CN101063412B (en) | 2012-06-13 |
Family
ID=38434044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2007101019043A Expired - Fee Related CN101063412B (en) | 2006-04-25 | 2007-04-25 | Nested turbine bucket closure group |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US7517195B2 (en) |
| EP (1) | EP1849963A3 (en) |
| JP (1) | JP2007292074A (en) |
| CN (1) | CN101063412B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103128704A (en) * | 2013-02-27 | 2013-06-05 | 哈尔滨汽轮机厂有限责任公司 | Assembly tool and application method of reverse-T-shaped blade-root groove blade with semicircular groove |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110158815A1 (en) * | 2009-12-28 | 2011-06-30 | General Electric Company | Non-circular pins for closure group assembly |
| US8714929B2 (en) | 2010-11-10 | 2014-05-06 | General Electric Company | Turbine assembly and method for securing a closure bucket |
| US9212563B2 (en) | 2012-06-06 | 2015-12-15 | General Electric Company | Turbine rotor and blade assembly with multi-piece locking blade |
| US9726026B2 (en) | 2012-06-06 | 2017-08-08 | General Electric Company | Turbine rotor and blade assembly with multi-piece locking blade |
Family Cites Families (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1415266A (en) * | 1919-08-30 | 1922-05-09 | Gen Electric | Elastic-fluid turbine |
| US1423466A (en) * | 1920-10-02 | 1922-07-18 | Westinghouse Electric & Mfg Co | Interlocking blade shroud |
| US2220918A (en) * | 1938-08-27 | 1940-11-12 | Gen Electric | Elastic fluid turbine bucket wheel |
| US2221685A (en) * | 1939-01-18 | 1940-11-12 | Gen Electric | Elastic fluid turbine bucket unit |
| US2844355A (en) * | 1954-05-19 | 1958-07-22 | Gen Electric | Turbine bucket wheel |
| BE655376A (en) * | 1963-11-07 | 1965-03-01 | ||
| FR2361531A1 (en) * | 1976-08-13 | 1978-03-10 | Europ Turb Vapeur | COMPRESSIBLE FLUID TURBINE |
| GB2006884B (en) * | 1977-10-04 | 1982-01-20 | Rolls Royce | Rotor assembly for a gas turbine engine |
| JPS60240804A (en) * | 1984-05-16 | 1985-11-29 | Hitachi Ltd | Moving blade |
| DE3528640A1 (en) * | 1985-06-28 | 1987-01-08 | Bbc Brown Boveri & Cie | Blade lock for rim-straddling blades of turboengines |
| US4702673A (en) * | 1985-10-18 | 1987-10-27 | General Electric Company | Method for assembly of tangential entry dovetailed bucket assemblies on a turbomachine bucket wheel |
| US4878811A (en) * | 1988-11-14 | 1989-11-07 | United Technologies Corporation | Axial compressor blade assembly |
| JP2000220405A (en) * | 1999-01-28 | 2000-08-08 | Hitachi Ltd | Turbine rotor blade |
| US6428279B1 (en) | 2000-12-22 | 2002-08-06 | General Electric Company | Low windage loss, light weight closure bucket design and related method |
| US6416286B1 (en) | 2000-12-28 | 2002-07-09 | General Electric Company | System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets |
| US6755618B2 (en) * | 2002-10-23 | 2004-06-29 | General Electric Company | Steam turbine closure bucket attachment |
| US6893224B2 (en) | 2002-12-11 | 2005-05-17 | General Electric Company | Methods and apparatus for assembling turbine engines |
| US6761537B1 (en) | 2002-12-19 | 2004-07-13 | General Electric Company | Methods and apparatus for assembling turbine engines |
| US6827554B2 (en) | 2003-02-25 | 2004-12-07 | General Electric Company | Axial entry turbine bucket dovetail with integral anti-rotation key |
| US7261518B2 (en) * | 2005-03-24 | 2007-08-28 | Siemens Demag Delaval Turbomachinery, Inc. | Locking arrangement for radial entry turbine blades |
-
2006
- 2006-04-25 US US11/380,049 patent/US7517195B2/en not_active Expired - Fee Related
-
2007
- 2007-04-20 JP JP2007111579A patent/JP2007292074A/en active Pending
- 2007-04-23 EP EP07106734A patent/EP1849963A3/en not_active Withdrawn
- 2007-04-25 CN CN2007101019043A patent/CN101063412B/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103128704A (en) * | 2013-02-27 | 2013-06-05 | 哈尔滨汽轮机厂有限责任公司 | Assembly tool and application method of reverse-T-shaped blade-root groove blade with semicircular groove |
Also Published As
| Publication number | Publication date |
|---|---|
| US7517195B2 (en) | 2009-04-14 |
| EP1849963A2 (en) | 2007-10-31 |
| EP1849963A3 (en) | 2011-03-02 |
| US20070248464A1 (en) | 2007-10-25 |
| JP2007292074A (en) | 2007-11-08 |
| CN101063412B (en) | 2012-06-13 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120613 Termination date: 20140425 |